BR0301686A - Single-engine connection aircraft engine mount - Google Patents

Single-engine connection aircraft engine mount

Info

Publication number
BR0301686A
BR0301686A BR0301686-2A BR0301686A BR0301686A BR 0301686 A BR0301686 A BR 0301686A BR 0301686 A BR0301686 A BR 0301686A BR 0301686 A BR0301686 A BR 0301686A
Authority
BR
Brazil
Prior art keywords
ear
flanges
screw
screw hole
motor
Prior art date
Application number
BR0301686-2A
Other languages
Portuguese (pt)
Other versions
BR0301686B1 (en
Inventor
John Alan Manteiga
Christopher James Wilusz
Cornelius Harm Dykhuizen
Original Assignee
Gen Electric
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Gen Electric filed Critical Gen Electric
Publication of BR0301686A publication Critical patent/BR0301686A/en
Publication of BR0301686B1 publication Critical patent/BR0301686B1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Prevention Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Transmission Devices (AREA)

Abstract

"SUPORTE DE MOTOR DE AVIãO COM LIGAçãO DE EMPUXO SIMPLES". A presente invenção refere-se a um suporte (20) para montagem de um motor de avião (10) em uma aeronave que inclui uma armação de montagem (46) tendo primeiro e segundo flanges (48, 50) espaçados a uma distância predeterminada. Cada um dos primeiro e segundo flanges (48, 50) tem um buraco de parafuso (70) nele formado. Uma ligação de empuxo simples (56) é conectada em uma extremidade à armação de montagem (46) e na outra extremidade ao motor (10) e serve com o curso de carga axial primário para o motor (10). Uma orelha (68) formada na caixa de motor (38) é disposta entre os primeiro e segundo flanges (48, 50) e tem uma espessura que é menor do que a distância entre os primeiro e segundo flanges (48, 50). A orelha (68) tem um buraco de parafuso (70) nela formado. Um parafuso (72) se estende através dos buracos de parafuso (70) nos primeiro e segundo flanges (48, 50) e a orelha (68) para conectar a orelha (68) aos primeiro e segundo flanges (48, 50). O buraco de parafuso (70) na orelha (68) é maior em diâmetro do que o parafuso (72) para permitir que a orelha (68) deslize axialmente ao longo do parafuso (72). Os primeiro e segundo flanges (48, 50), a orelha (68) e o parafuso (72) proporcionam uma disposição de falha de segurança de espera (66) para reatuar cargas axiais mediante falha da ligação de empuxo simples (56)."SIMPLE PUSH CONNECTION AIRPLANE SUPPORT". The present invention relates to a holder (20) for mounting an aircraft engine (10) on an aircraft including a mounting frame (46) having first and second flanges (48, 50) spaced at a predetermined distance. Each of the first and second flanges (48, 50) has a screw hole (70) formed therein. A single thrust connection (56) is connected at one end to the mounting frame (46) and at the other end to the motor (10) and serves as the primary axial loading stroke for the motor (10). An ear (68) formed in the motor housing (38) is disposed between the first and second flanges (48, 50) and has a thickness that is less than the distance between the first and second flanges (48, 50). The ear 68 has a screw hole 70 formed therein. A screw (72) extends through the screw holes (70) in the first and second flanges (48, 50) and the ear (68) to connect the ear (68) to the first and second flanges (48, 50). The screw hole (70) in the ear (68) is larger in diameter than the screw (72) to allow the ear (68) to slide axially along the screw (72). The first and second flanges (48, 50), the ear (68) and the bolt (72) provide a standby safety fault arrangement (66) for reacting axial loads upon single thrust connection failure (56).

BRPI0301686-2A 2002-06-28 2003-06-27 aircraft engine mount with single push connection. BR0301686B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/185,922 US6607165B1 (en) 2002-06-28 2002-06-28 Aircraft engine mount with single thrust link

Publications (2)

Publication Number Publication Date
BR0301686A true BR0301686A (en) 2004-08-24
BR0301686B1 BR0301686B1 (en) 2012-02-07

Family

ID=27733962

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0301686-2A BR0301686B1 (en) 2002-06-28 2003-06-27 aircraft engine mount with single push connection.

Country Status (6)

Country Link
US (1) US6607165B1 (en)
EP (1) EP1375348B1 (en)
JP (1) JP4498694B2 (en)
BR (1) BR0301686B1 (en)
CA (1) CA2432851A1 (en)
DE (1) DE60323008D1 (en)

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Also Published As

Publication number Publication date
CA2432851A1 (en) 2003-12-28
EP1375348A3 (en) 2005-10-05
BR0301686B1 (en) 2012-02-07
DE60323008D1 (en) 2008-10-02
JP2004052762A (en) 2004-02-19
EP1375348A2 (en) 2004-01-02
JP4498694B2 (en) 2010-07-07
US6607165B1 (en) 2003-08-19
EP1375348B1 (en) 2008-08-20

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